| Abstract: | We consider the two‐dimensional high/moderate Reynolds‐number flow around a slender airfoil at small angles of attack. Special emphasis is placed on leading edge separation and the associated breakdown of the steady solution of the governing equations. A comparison between the predictions of the viscous/inviscid interaction theory of marginal separation, see e.g. 3], and the results of Navier–Stokes computations with DLR's ‘TAU’–code 2] shows excellent quantitative agreement concerning the location, size of the separation bubble and even the limiting maximum value of the angle of attack, up to which solutions by means of the particular approaches can be found. |
